Published February 1972
| Published
Journal Article
Open
An experiment on the adiabatic compressible turbulent boundary layer in adverse and favourable pressure gradients
- Creators
- Lewis, J. E.
- Gran, R. L.
- Kubota, T.
Abstract
A wind-tunnel model was developed to study the two-dimensional turbulent boundary layer in adverse and favourable pressure gradients with out the effects of streamwise surface curvature. Experiments were performed at Mach 4 with an adiabatic wall, and mean flow measurements within the boundary layer were obtained. The data, when viewed in the velocity transformation suggested by Van Driest, show good general agreement with the composite boundary-layer profile developed for the low-speed turbulent boundary layer. Moreover, the pressure gradient parameter suggested by Alber & Coats was found to correlate the data with low-speed results.
Additional Information
© 1972 Cambridge University Press. Received 14 July 1971 and in revised form 20 September 1971. Published online: 29 March 2006. The authors gratefully acknowledge the support of the Advanced Research Projects Agency and the U.S. Air Force Space and Missile Systems Organization under Contract FO4701-71-C-0040 and the co-operation of the staff of the von Kámán Gas Dynamics Facility at AEDC where the experiments were performed.Attached Files
Published - LEWjfm72.pdf
Files
LEWjfm72.pdf
Files
(2.0 MB)
| Name | Size | Download all |
|---|---|---|
|
md5:9149b6b56b7b7a0911d39f3f60232d41
|
2.0 MB | Preview Download |
Additional details
- Eprint ID
- 32941
- Resolver ID
- CaltechAUTHORS:20120806-110003896
- Advanced Research Projects Agency
- FO4701-71-C-0040
- Air Force Space and Missile Systems Organization
- Created
-
2012-08-06Created from EPrint's datestamp field
- Updated
-
2021-11-09Created from EPrint's last_modified field